Flow Analysis Around Aircraft with Propeller Effect
I want to see flow around aircraft propeller with propeller effect. I created a fan disk at where the propeller suppose to be. I get fluent analysis but at zero angle of attack CD is negative it is around -0.155 and Cm is around -0.5. But Cl is very close the without propeller results. What can I do to get correct results of Cd and Cm?
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